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SECTION III.  AIRCRAFT FILL AND TEST PROCEDURES
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TM-1-4920-446-13P Hydraulic System Test Stand Type D-8A P/N 7459 Manual
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Aircraft System Test
TM 1-4920-446-13 & P a.  Ensure the test stand has been prepared for operation (paragraph 2-5) and is properly connected to the aircraft. Set reservoir shutoff valve (9, Figure 2-2) to the closed position. NOTE For correct fill procedures, refer to the technical publication which applies to the aircraft being serviced. b.  Adjust the pump flow limit adjust control (11) for minimum flow and activate the test stand (25). c.  Open flow control valve (12 or 13). d.  Set selector valve (8) in the LP filter out position. e.  Slowly close the HP bypass valve (7). f.  Set the compensator control (6) and HP relief valve (10) for the pressure required for the particular aircraft. g.  Slowly increase the volume output of the test stand with the flow limit adjust control (11) in accordance with air- craft requirements. Do not exceed the rated volume flow for the aircraft system pumps.  Refer to the aircraft publication for pump ca- pacities. h.  Aircraft controls must be continually cycled to ensure all air is bled from the system and to prevent heat build up. i.  Add hydraulic fluid to the test stand during filling to maintain the reservoir over one-half full. j.  When bleeding is complete, use standard operating procedures to shut down the test stand (paragraph 2-8). 2-14.  Aircraft Testing Procedures. a.  Connect hoses to the aircraft. b.  Set reservoir shutoff valve to open. c.  Set flow control (12 or 13) to open. d.  Set HP bypass valve (7) to closed. e.  Operate the test stand in the manner described in paragraph 2-7. f.  Set the HP compensator control (6) to the desired pressure. 2-9

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